Aerial pick-up system



Jan. 26, 1965 R. B. COTTON 3,167,303

AERIAL. PICK-UP SYSTEM Filed March 12, 1965 4 Sheets-Sheet 1 Robert 8. Cotton ATTORNEY Jan. 26, 1965 R. B. COTTON 3,167,303

AERIAL PICK-UP SYSTEM Filed March 12, 1963 4 Sheets-Sheet 2 FIG.9.

INVENTOR ATTORNEY Robert 8. Cotton- Jan. 26, 1965 R. B. COTTON AERIAL PICK-UP SYSTEM 4 Sheets-Sheet 3 Filed March 12, 1963 INVENTOR Robert B. Cotton NTQE o! nwv Pm vn H.

mm vm H 0? ATTORNEY Jan. 26, 1965 R. B. COTTON 3,167,303

I AERIAL PICK-UP SYSTEM Filed March 12, 1963 4 Sheets-Sheet 4 FIG .l6.

mvsmon Robert 8. Cotton FIGJ3. BY 4: v

ATTORNEY 3,167,303 AERIAL PICK-UP SYSTEM Robert E. Cotton, Media, Pa, assignor to All American Engineering (Company, Wilmington, Deh, a corporation of Delaware Filed 12, 1963, Ser. No. 264,611 3? Claims. (El. 258-12) This invention relates to aerial pick-up systems and more particularly to pick-up systems wherein an aircraft can pick up cargo or the like from a surface station while the said aircraft is maintaining altitude and airspeed.

It is an object of this invention to provide an aerial pick-up system having light-weight ground equipment which can be easily handled by a single operator.

It is another object of this invention to provide an aerial pick-up system wherein the aircraft may be at altitudes of up to two hundred and fifty feet or more above the surface station from which the cargo is to be picked up.

Another object of this invention is to provide an aerial pick-up system wherein the kinetic energy of the aircraft is used to provide the energy required to effectuate the pick-up.

Another object of this invention is to provide anaerial pick-up system wherein an auxiliary pick-up line suspended from an airborne target means is utilized to accelerate a main pick-up line, attached at one end to the cargo, to the aircraft and the main pick-up line is subsequently used to deliver the cargo into the aircraft.

Still another object of this invention is to provide an aerial pick-up system wherein an auxiliary pick-up line suspended from an airborne target means is utilized to accelerate a main pick-up line, attached at one end to the cargo, to the aircraft and the main pick-up line is subsequently used to deliver the cargo into the aircraft; and wherein a first drag parachute is utilized to accelerate said auxiliary and main picloup lines to said aircraft and a second drag parachute is utilized to accelerate said cargo to said aircraft.

Still another object of this invention is to provide an aerial pick-up system including an aircraft and a novel drag parachute and capstan means in said aircraft.

Still another object of this invention is to provide an aerial pick-up system including an aircraft and a novel drag parachute and capstan means in said aircraft, wherein said drag parachute and capstan means are energized by the kinetic energy of said aircraft.

Still another object of this invention is to provide an aerial pick-up system including an aircraft and a novel drag parachute and capstan means in said aircraft; and

novel control means on said drag parachute and capstan means to obtain variable reel-in speed of a cargo as it approaches the aircraft.

Yet another object of this invention is to provide an aerial pick-up system for human cargo wherein optimum safety conditions are provided.

Yet another object of this invention is to provide an aerial pick-up system wherein the equipment used is simple, light in weight and inexpensive.

Still another object of this invention is to provide an aerial pick-up system including an aircraft and ground equipment wherein the means of making contact with the ground equipment by the aircraft provides optimum reliability and safety under all conditions of operation of the aircraft.

Still another object of this invention is to provide an aerial pick-up system, wherein means is provided in the United States Patent Bihifihi Patented Jan. 26, 1965 ice These and other objects of this invention will become more fully apparent with reference to the following specification and drawings which relate to several preferred embodiments of the invention.

In the drawings:

FIGURE 1 is a perspective of the assembled surface station equipment of the invention;

FIGURE 2 is a perspective of the airborne equipment of the invention;

FIGURE 3 is an enlarged front elevation of the capstan assembly shown in FIGURE 2;

FIGURE 4 is a side elevation of the capstan assembly of FIGURE 3;

FIGURE 5 is an enlarged detail in perspective of the ring hook assembly shown in FIGURE 2;

FIGURE 6 is an enlarged detail in perspective of the safety wedge assembly shown in FIGURE 2;

FIGURE '7 is a schematic representation of a drag chute and a drag control means for the said chute;

FIGURE 8 is a schematic of the invention immediately prior to the initiation of a pick-up cycle;

FIGURE 9 is a schematic of the invention in a stage in the pick-up cycle subsequent to that of FIGURE 8;

FIGURE 10 is a schematic of the invention in a stage in the pick-up cycle subsequent to FIGURE 9;

FIGURE 11 is a schematic of the invention in a stage in the pick-up cycle subsequent to FIGURE 10;

FIGURE 12 is a schematic of the invention in a stage in the pick-up cycle subsequent to FIGURE 11;

FIGURE 13 is a schematic of another embodiment of the ground station equipment of the invention;

FIGURE 14 is a schematic of the embodiment of FIG- URE 13 in a final stage of the pick-up cycle;

FIGURE 15 is a partial schematic of a system for picking up heavy cargo; and

FIGURE 16 is an operational schematic of the heavy cargo system of FIGURE 15.

Referring in detail to the drawings, and more particularly to FIGURE 1, the ground station It is shown as including an airborne balloon target 12 tethered via an integral bridle 14 and leader 16 to the apex of a first drag parachute l8, hereinafter described as the pilot drag chute 7.8. The said pilot chute i8 is tethered via its shroud lines 2% to one end of a pilot pick-up line 22, the other end of the pilot line 22 being connected to a coupling rin assembly 24 which joins the pilot line 22 to one end of a main pick-up line 26. The other end of the main pick-up line 26 is connected with a cargo 28 which is to be picked up by the system of the present invention. A frangible link 39 or the like is connected between the main line 26 adjacent the coupling ring 24 and a land anchor 32 whereby the balloon target 12 is tethered to the ground 34.

The main pick-up line may be contained on the ground in a faking box F, as shown in dotted lines in FIGURE 1.

Referring now to FIGURE 2, the airborne equipment 36 in the aircraft 35 will now be described.

A dependent pick-up loop 40 is effected by a closed loop of line 42 having a centrally located ring-hook assembly 44 in the lowermost portion thereof. The loop 4% is kept in open position by means of a pair of dependent parallel pick-up poles 4-5 and 48 which are mounted on the cargo platform 5t of the aircraft 38 by means of cylindrical pole mounts 52 and 54, respectively. The pole mounts 52 and 54 are at right angles to the respective pickup poles 46 and 48 and are rotatably mounted in cylindrical housings 56 and 5% which are horizontally and transversely fixed on the cargo platform 50 of the aircraft 38. The pick-up poles have a plurality of spring clips 60 distributed along their respective lengths in which the line 42 forming the pick-up loop 40 is retained. The line 42 is composed of a material whereby the said line 42 is i. which has a low coeflicientof surface frictionp;

o V I a flexible but resists kinking as will be hereinafter more fully described.

The pick-up poles 46 and 48 are respectively provided adjacent their outermost tips with drag plates 62 and 64 which balance the dnag load, caused by the airstream in which the said poles are positioned, to maintain the poles in the lowered position shown in FIGURE 2; Manual positioning means for the 'poles 46 and 48 such asf the handles 66 and 68, respectively, on the pole mounts 52and 54 are provided.

The loop line 42 extends from the upper end of: the

loop over a buffer or guide roller 60 on 'the rear edge of the cargo platform ,50, and thence through-a one-way safety wedge 72 to the capstan or main drum' 74 of a capstan assembly 76 whichjis mounted on the" cargo plat- 4 V Asshown, the pilotline 22 is reeved around the V-tube 122 at the apex thereof. This causes the coupling ring assembly 24 to /approach the spring grapple means 124 during the pick-up cycle. V e

The coupling ring assemblyv 24 comprises a metal "ring 128 confined in a basket or sheath 130'defined by a pluform 50 of the aircraft 38. Several turns of the loop line 3 ,42 are made around the capstan 74 for a purpose to be 7 hereinafter described.

Referring now to' FIGURES '3 and 4, the capstan assembly 76 will now be described in more detail;

The capstan 74 is keyed to ahollow central shaft78 in the capstan \assembly76, the shaft 78 being journalled for rotation in bearing means 80 mounted in a concentric;

housing 82; The housing-82 is integral with afixed base means 84 which is bolted-or otherwise suitably affixed to the cargo platform 50. y

rality of longitudinallyldisposed line sections132 which engage the ring12 6 at spaced points on its periphery to keep the plane of the ring 126 perpendicular to the pilot and; main pick-up lines 22aind 26, respectively. I

'As shown in FIGURE 6, the preferred embodiment of the main pick-up line 26, as Well as all of the other lines not "shown, is in the form of a flat synthetic tape such as that commonly fabricated from nylon.

The safety wedge 72 is shown as comprising twoa'ectangular keeper blocks 134 having inner planar surfaces conformally shaped to receive two wedge-shaped brake shoes 136 therebetween which are arranged to increase the drag exerted thereby on the main pick-up line 26 if it Adjacent the-opposite end of the shaft 78' from the, V capstan74,ca brake housing 86 is mounted on the shaft 4 housing 82 which houses any suitable friction brake means".

88 for applying a selective braking action to theshaft 7 8.

An operating .brake handle 90 is provided to actuate the friction brake means 88. r

At the opposite end of the shaft 78, adjacent the capstan 74, an auxiliary or control line drum 92 is mounted fo r .both sliding movement and free rotation on the, said shaft- 78. A drag link 94 is connected from a telescoping en larged end ,cap 98 on the tip' of the shaft"78,'juxtaposed i with the outer face of the control line drum 92, through the interior of: the shaft 78 to the other end thereof whereit is connected intermediate the ends of an openating lever .100. The lever 100 is pivoted at one end by apivot means 102 onz a fixed stanchion 104 or the like on the base means 84 of the "capstan assembly 76.. The control handle 100 is pivoted on the pivot means 102. such-that movement of the handle 100 is efiectedlongitudinally of the shaft 78." i

A plurality of friction brake pads or discs 106' are tends to movefrom'left to right as shown. This direction is respresentative of that which would take the cargo 28 shown which 'is'connected by its shroud lines 142jand a terminal or couplingring 144 to the loop line 42, the loop line 42 being Wound'on the capstan 74.

T he'apex 146 of main drag chute 140 is connected with one end of a drag control line l48 which extends through the terminal ring 144 on the said chute140 to the control line drum 92 of the capstanassernbly 76 where it is wound on thesaid drum 92.. I I

Referring now to FIGURElSyanothe'r embodiment of aground station 10'is shown as including, in addition to all of the elements of the ground station '10 of FIGURE 1,

V a personnel parachute 150 connected with a human cargo mounted integral with the inner end face of the controlline drum and are adapted to be selectively engaged, with;

the adjacent end face of'the capstan 74 as Will be hereinafter more fully described.

On the opposite end face ofithe capstan 7 4,a ring gear 108 is integrally and symmetrically mounted. A; g pawl means 110 mounted on a rocker arm 112 which as loads weighing mo're than four hundred pounds, the inherent energy absorotion characteristics .of the main pick-up line 26 is insufficient to properly compensate for is in turn mounted on the base means 84 is provided to selectively prevent turning of the capstan by engaging the teeth 114 of the ring gear 108.

A spur gear rewind means 116 is generally shown which he I cooperates with a rewind handle "118 and the teeth 114 of the ring gear 108 to provide a manual rewind means'for,

the capstan assembly 76.

Referring back to FIGURE 2, a block and tackle as sembly 120 is provided in the aircraft 38 adjacent the v of a suitable tow line 160 which is reeved on the capstan capstan assembly 76, whereby the cargo 28 may be finally brought aboard after being picked-up and brought to a position irrnnediatelyadjacentthe rear end of the 'cargo platform 50.;

' Referring now .to

'28 "by its conventional harness" and shroud lines. not shown, and connected by itsapex,'not shown, to the end of the main pick-up line 26. A lift parachute152 is tethered in open condition 'to the main pick-up line 26 via its shroud lines .154 and a tethering means 156 located adjacent the apex of the personnel parachute 150.

Heavy cargo pick-up i For heavy cargo loads at the grou nd station 10, such the high transient loads incurred during initial acceleration of the cargo 28 from the ground station 10 toward the vided for absorbing the said transient loads.

Referring toFIGURE 15 one preferred embodiment "aircraft 38. Thus, some additional means must be pro- 10f such an energyab'sorber will now bedescribed.

A retaining'hook 158 is integrally connected to the rear edge of the cargo deck or ramp 50 of the aircraft 38. The main drag parachute is connected to one end 1 assembly 7,.6=and terminates at its other end in an integral FIGURE -5, the ring hook assembly '44 is showninmore'detaillasicomprising a V-tube 122 having an-arrow-shaped, spring-like, grapple means 124. extendinggfrom the apex thereoffl TheV-tube122 is connected with the loop-line,42 by passing the "line 42- through the tube and bonding it to the tubeends 7 126. e .-V-tube 122 is coated with Teflon or other synthetic The retaining :ring 162 retaining ring 162 which is engaged with theretaining hook:158 on the load deck 50. The drag of the main drag chute 140 tensions'the tow line 160 and causes the ,said retaining ring '162 jto remain securely, on the said retaining hook 158.

may be of either a rigid ring; or resilient, loop construction as lon'glas its strength is suificient;

V e e is further-connected into the pick-up system on the aircraft-38 by attaching the upper end ofthepick-up. loop 42 thereto. The retaining ring Operation Referring now to FIGURES 8, 9, 10, 11 and 12, the

operation of the invention will now be described.

The first step in initiating a pick-up cycle, once the ground station has been erected to place the airborne target balloon 12 in the air, is to fly the aircraft 33 directly into the balloon 12 such that the nose of the said aircraft 38 will burst the balloon 12.

The pick-up loop 49 is suspended at a sufiicient distance below the aircraft 33, via the poles 46 and 43, so that the pilot drag chute 18 will pass through the loop 4%, and, as shown in FIGURE 5, the pilot line 22 will reeve around the V-tube 122 of the ring-hook assembly 44. The reason for the anti-kinking characteristics of theloop line 42 will now become apparent. If the pilot line 22 engages the loop 40 off-center such that there is line-to-line engagement between the loop line 42 and the said pilot line 22, the loop line 42 must be of sufficient stiffness to serve as a guide for the pilot line 22. Thus, the pilot line 22 will always eventually end up reeved around the V-tube 122 of the ring-hook assembly 44. If the loop line 42 should kink and grab the pilot line 22 the system would not function properly.

The pilot drag chute 18 now opens and applies a drag load on the pilot line 22 which is sufi'icient to accelerate the main pick-up line 26 toward the aircraft 38 as the pilot drag chute l8 accelerates away from the said aircraft The drag load generated causes the pick-up loop 40 to be disengaged from the pick-up poles 46 and 48 by forcing the loop line 42 out of engagement with the spring clips 60 on the said pick-up poles.

' After the pilot line 22 has substantially passed through the ring-hook assembly 44, the coupling ring 128, see FIGURE 5, of the coupling ring assembly 24 is caused to be impaled upon the spring grapple means 124 of the ring-hook assembly 44. Since the grapple means 124 is arrow-shaped, the ring 128 cannot back off of the said grapple. Also, because of the dimensions of the V-tube 122, the ring 128 cannot proceed forward on the ringhook assembly 44 thus stopping the acceleration of the pilot line 22, by means of the pilot drag chute 18.

The ilot line 22 is very light in weight and strength compared to the main pick-up line 26 so that a small balloon target 12 is sufficient to maintain it above the ground 34. Its strength is only sulficient to lift and accelerate the main pick-up line 26 to the aircraft 38.

Thus, the load on the pilot line 22 caused by the pilot drag chute 18 is suddenly increased above the maximum permissible load for the said pilot line 22 and the pilot line 22 is caused to rupture as shown in FIGURE 10. However, the main pick-up line 26 is now connected with the loop-line 42 via the ring hook assembly 44 and the coupling ring assembly 24 and once the main line 26 is fully tensioned by the aircraft 38, the cargo will be accelerated from the ground 34 and trail behind the aircraft 3:3 as shown in FIGURE ll. By using a synthetic pick-up line, the resilient properties of the line and the drag thereon during a pick-up cycle are sufficient to insure a smooth safe acceleration rate of the cargo 28 I toward the aircraft 38.

connected to the loop line 42 after it has been recved around the capstan 74 for several turns, is released from the aircraft 38 and permitted to trail behind as generally shown in FIGURE 12.

Since the friction brake 88 is engaged with the capstan "shaft 78 and the locking pawl 110 is engaged with the teeth 114 of the ring gear 108, the capstan is prevented from turning under the torque generated by the drag of the main drag chute 140.

Now, the friction brake 88 is relieved slightly and the locking pawl 11%) is disengaged to permit the capstan 74 to turn and bring the V-tube 122, grapple means 124 and coupling ring 128 up to the safety wedge 72. The safety wedge 72 is then opened to permit this ring-hook assembly 44 and coupling ring 128 to pass through, after which the wedge 72 is reclosed on the main pick-up line 26 and the said ring-hook assembly is permitted, by regulation of the friction brake 88 to pass around the capstan 74 and back out of the aircraft 38 under the pull of the main drag chute 140.

The friction brake 88 is now disengaged to permit the main drag chute 14d, capstan 74 and the main pick-up line 26 to reel-in the cargo 28 to the aircraft 38 at a high rate of speed.

The reel-in speed is controlled by the drag-control line 143 between the control line drum 92 on the capstan assembly '76 and the apex 146 of the main drag chute 140.

As shown in FIGURES 3 and 7, the control line drum 22 is of a smaller effective diameter than the capstan 74, whereby the control line 143 causes the control drum 92 to turn at a higher r.p.m. than the capstan 74 as it is payed-out with the main drag chute 149. Thus, there is relative motion between the capstan 74 and the control drum 22.

Therefore, by applying the proper pressure to the brake lever ltltl the control drum 92 and the friction pads thereon will be forced, via the drag link 94, into engagement with the capstan 74. Thus, the reel-out rate of the drag control line 148 may be varied from the reel-out speed of the main drag chute 140 downward and the said chute 14% may be selectively spilled to vary the drag generated thereby and hence, the reel-out speed thereof.

The reel-out continues until the cargo 28 is in a position where the block and tackle may be connected therewith to load it into the aircraft 38 and complete the pick-up cycle.

The main pick-up line 26, loop line 42 and main drag chute 14%) are now in tow behind the aircraft 38. This assembly may be expended in the interest of speed or in the alternative, the control line 148 may be used to completely spill the main drag chute and the manual reel-in handle 11$, spur gear assembly 116 and ring gear 188 may be employed to retrieve it. Power rewind means may, of course, also be employed.

With reference to the embodiment of FIGURE" 13, the pick-up cycle operation is the same as that shown in FIGURES 8, 9, 10, 11 and 12 except for the presence and function of the lift parachute 1S2.

As shown in FIGURE 14, when the cargo 28' is accelerated by the main pick-up line 26, the lift chute creates a drag force which assures a rapid vertical rise of the human cargo 23', whereby in rough or overgrown terrain the chance of injury is minimized.

Referring now to FIGURES 15 and 16, the operation of the heavy cargo embodiment of the invention will now be described.

The main drag chute 140 is payed-out from the capstan assembly 76 and held at a fixed distance behind the aircraft 38 via the tow line and the retaining ring 162 on the integral retaining hook 158. The pilot line 22 is then engaged by the ring-hook assembly 44 and the coupling ring 24 on the main line 26 issubsequently cngaged as hereinbefore described.

(However, when the slack has been taken-up in the main line 26, the inertia mass of the heavy cargo 2? acts to pull the retaining ring 162 off the retaining hook 158 and suddenly subject the main drag chute 140 to the full cargo load including the said inertia of the cargo 28.

Thus, the transient loading causes the main drag chute $40 to come towards the aircraft 38 until the energy of inertia of the cargo 28 has been fully absorbed, at which point the main drag chute I40 reverses its direction and accelerates the cargo 28 towards the aircraft 38.

The reel-in speed may then be controlled as hereinbefore described.

pick-up system which is light in weight and foolproof in "areas operation and which satisfies a long felt need in the aerial pick-up art for a system which permits the'flying of an aircraft at normal altitudes and speeds during the pick-up cycle.' All of the energy required to accelerate the pilot line, pick-up line and cargo toward the aircraftisderived from the kinetic energy of the aircraft by means of drag parachutes.

his to be understood that the embodiments of this inv vention shown and described herein are for the sake of ex ample only'and are not intended to limit the scope of the surface station, first pick-up means on said aircraft,'a cargo at said surface station to be delivered to said aircraft via said first pick-up means while'said aircraft is maintaining normal altitude and airspeed and second pick-up means at said surface station engageable'by said firstpick-up means,

including a pick-up line connected at one end to said cargo,

a pilot line connected at one end to the other end of said pick-up line, an airborne'target means anda drag p'arachute, said airborne targetrneans beingtethered' tofthe other end of said pilot line by means of said :drag' parachute. I

2, The invention defined in claim 1,wherein said pilot line .is of substantially lesser strength'and weight than said pick-upline and wherein both said pilot line andsaidpicb' up line are composed of resilient synthetic fibers.

. 8 body, airborne pilot means connected. with said tow means and extending into the path of said airbornerbody and being of sufiicient strengthandweight to withstand acceleration loads'on saidtow. means, said pilot means including drag means. integral, therewith adjacent said airborne body'and means on said airborne body adapted to-engage said pilotmeans adjacent to said drag means. 9. An aerial pick-up system comprising an aircraft, a surface station, a cargo at said surface station to be picked up and delivered to said aircraft while said aircraft is maintaining normal altitude and .air speed, first pick-up means on said aircraft including a dependent pick u'p loop, capstan means 'and'first drag means, said pick-up loop including an integral extension reeved around said capstan means andconnected withsaid first 'drag'means; and second pick-up means at said surface 7 station. comprising an airborne target'means tethered to said surface station, a pick-up line connected with said cargo, a pilot line connected with said pick-up line and 201' i second drag meansinterconnecting said pilot line and said target means, said pilot line-being tethered to said surface station to constrain said target means and said drag means ther'eabove and being adapted: to be engaged by said pick-up loop adjacent said second dragmeans. 2 l

10.,Their1vention defined in claim 9, wherein said first and second" drag means comprise first andsecond.

parachute means, respectively, said first drag means being of sufficient size to accelerate, said pick-upline and said 3. The invention defined .in claim l, wherein said first pick-up means further includes a pick-up loop dependent from said aircraft having line quide means for said pilot line and a first coupling means on said line quide means cargo toward, said aircraft and said second drag means being of sufficient size to accelerate said pick-up line and said pilot line to'ward said aircraft. I

11. Theinvention defined inclaim 9, wherein said pilot line is of substantially lesser'strength and weight than and wherein said second pick-up means furtherinclud'es' a second coupling meansinterconnecting said'pilot'line and said. pick-up line adaptedto interconnect with said first coupling means when'said pick-up line has been aecelerated into juxtaposition with saidline guide means by saidpilotlinep 4.1 116 invention definedfin claim 3, wherein said line 7 1 guide means comprises a iV-shapedtub'ular memberintegral with said pick-up'loop and adapted to receive said I pilot line within the apex thereof; wherein said first'cou- V of "said V-shaped member, having one-way, engaging means thereon; and wherein said second coupling means inpick-up means on said aircraft, a surface station anda cargo at' said surface station to be'picked up by said aircraft, the combination at "said surface station of 'an' airborne target means, drag-means suspended below said interconnecting said pilot 'linepand said cargo, said pilot line andsaiddrag" means cooperating with said pick-up means to accelerate said' pick-up line toward said aircraft.

6. The invention defined in claim '5, wherein said pilot pling means comprises an integralrextension of the apex 1 said pick-up line andwherein both said pilot line and said ,pick-upgline are composed ofresilient synthetic'fibers.

12."The invention defined in claim '9', wherein said capstan means funther includes 1 selective drag control means'for said first drag means.

The invention defined in claim 9, wherein said first drag means comprises, "a parachute having a canopy and shroudlines, said shroud lines beingconne'cted'with I said. extension of said pick-up 1oop,fa'nd wherein said cap stan mea'ns further-includes selective drag control means for saidi'firstjdrag means comprising a control line .con-

nected' atone end with the apex of said 'can'opy'and differential pay-out means on saidcapstan means, said contrqliline being woundthereon, at the other end thereof,

whereby saidfcanopy canbeselectively spilled to vary thedrag exerted by saidfirst drag means.

145 The invention defined in claim 9, wherein said ffirstpick-up means further includes a one-way brake target means, a pilot line tethering said drag means and target means tosaidsurfa'ce station, and a pick-up, line a meansintermediate said pick-up loop and said capstan me s I 15. The"invention defined inf'claim- 9, wherein said pick-uploop fur therincludes line-guide means for said pilot line and a first coupling' means on saidline-guide means, and wherein said second pick-up'rnean's further 7 ,includes asecond coupling .means'interconnecting said pilot line .and said pick-up line adaptedto interconnect with said first coupling.means when said pick-up linehas I been accelerated into juxtaposition with said line guide line is of substantially lesser strength W and ,weight'than means comprises a parachute having. a' canopy andshroud lines, said canopy being. connected at its apex with said target means and said shroud lines being connected with said pilot line. i i

8. Means foryacceleratingv-ianinitially fixed su rfacfe body is, a.moving I airborneflbody. utilizing the kinetic energy of said'airb'or'ne body, comprising tow means'conlnected withls'aid surface body f 'of sufficient strength-.and..

J weight to withstand acceleration loads on 'saidfsurface.

' 16.'The invention definedfin claimf15, wherein said line guide means comprises a V-shaped tubular member integral with said pick up loop ,and adapted to receive said pilot line within the apex thereof; wherein said first couplingmeans comprises an integr al extension of the apex of said l-shaped member having one way engaging means thereon; and whereinsaidsecond coupling means includes, an in-line coupling element at the juncture of saidfpilo t lin e and said picbuplineadapted-to; interlock with said" one-way engaging means.

1 7:.'T;; Ir1 .a'naerial, .piclc-fup system comprising an ,aircraft, a surface station and" a cargo at said surfacestation 9 including a pick-up line adapted to beengaged with means on said aircraft and constrained in tow behind said aircraft, means on said aircraft for bringing said in tow cargo into juxtaposition with said aircraft comprising a pick-up loop interconnected with said pick-up line, capstan means, and drag means, said loop including an integral extension reeved on said capstan means and connected with said drag means.

18. The invention defined in claim 17, wherein said capstan means further includes drag control means for selectively regulating the drag of said drag means.

19. The invention defined in claim 17, wherein said first drag means comprises a parachute having a canopy and shroud lines, said shroud lines being connected with said extension of said pick-up loop, and wherein said capstan means further includes selective drag control means for said first drag means comprising a control line I connected at one end with the apex of said canopy and differential pay-out means on said capstan means, said control line being wound thereon at the other end thereof, whereby said canopy can be selectively spilled to vary the drag exerted by said first drag means.

20. In an aerial pick-up system including an aircraft, pick-up means on said aircraft, a surface station, an airborne .target means tethered to said surface station, a cargo at said surface station to be picked up by said aircraft, a pick-up line connected to said cargo, a pilot line connected with said pickup line, and a drag means interconnecting said pilot line and said airborne target means, said pilot line being tethered to said surface station to constrain said target means and said drag means thereabove, the method of picking up said cargo with said aircraft comprising the steps of flying said aircraft directly into said target means and rupturing said target means, engaging said pilot line with said pick-up means at a point below said drag means to thereby reeve said pilot line around said pick-up means, accelerating said pick-up line toward said aircraft with said pilot line by the kinetic energy derived from said aircraft by said drag means, securing said pick-up line to said pick-up means, rupturting said pilot line to thereby release said drag means and subsequently accelerating said cargo toward said aircraft by said pick-up line.

21. In an aerial pick-up system including an aircraft, pick-up means on said aircraft including a pick-up loop, capstan means and first drag means, said loop including an integral extension reeved on said capstan means and connected with said first drag means, a surface station, an

airborne target means tethered to saidsurface station, a

cargo at said surface station to be picked up and delivered to said aircraft, a pick-up line connected to said cargo, a pilot line connected with said pick-up line, and a second drag means interconnecting said pilot line and said airborne target means, said pilot line being tethered to said surface station to constrain said target means and said drag means thereabove, the method of picking up and delivering said cargo to said aircraft comprising the steps of dying said aircraft directly into said target means and rupturing said target means, engaging said pilot line with said pick-up means at a point below said second drag 7 means to thereby reeve said pilot line around said pick-up irreansaccelerating said pick-up line toward said aircraft 1 with said pilot line by the kinetic energy derived from said cargo into juxtaposition with said aircraft.

22. An aerial pick-up system comprising an aircraft,

a surface station, a cargo at said surface station to be picked up and delivered to said aircraft while said aircraft is maintaining normal altitude and air speed, first pick-up means on said aircraft including a dependent pick-up loop, capstan means and first drag means, said pick-up loop including an integral extension reeved around said capstan means and connected with said first drag means; and second pick-up means at said surface station comprising an airborne target means tethered to said surface station, a pick-up line connected with said cargo, a pilot line connected with said pick-up line and second drag means interconnecting said pilot line and said target means, said pilot line being tethered to said surface station to constrain said target means and said drag means thereabove and being adapted to be engaged by said pick-up loop adjacent said second drag means, and third drag means connected with said pick-up line at a point adjacent said cargo.

23. The invention defined in claim 22, wherein said first, second and third drag means comprise first, second and third parachute means, respectively, said first drag means being of sufiicient size to accelerate said pick-up line and said cargo toward said aircraft, said second drag means being of sufiicient size to accelerate said pick-up line and said pilot line toward said aircraft and said third drag means being of sufficient size to augment the lift imparted to said cargo by said pick-up line when acting in opposition to said first drag means.

24. Means for accelerating an initially fixed surface body to a moving airborne body utilizing the kinetic energy ofsaid airborne body comprising tow means connected with said surface body of sufficient strength and weight to withstand acceleration loads on said surface body, airborne pilot means connected with said tow means and extending into the path of said airborne body and being of sufiicient strength and weight to withstand acceleration loads on said tow means, said pilot means including first drag means integral therewith adjacent said airborne body, means on said airborne body adapted to engage said pilot means adjacent to said drag means and second drag means on said tow means adjacent said surface body t for augmenting the lift imparted thereto by said tow means.

25. In an aerial pick-up system including an aircraft, pick-up means on said aircraft, a surface station and a cargo at said surface station to be picked up by said aircraft, the combination at said surface station of an airborne target means, first drag means suspended below said target means, a pilot line tethering said drag means and target means to said surface station, and a pick-up line interconnecting said pilot line and said cargo, said pilot line and said drag means cooperating with said pickup means to accelerate said pick-up line toward said aircraft and second drag means connected with said pic. up line at a point adjacent said cargo.

26. In an aerial pick-up system comprising an aircraft, a surface station and a cargo at said surface station including a pick-up line adapted to be engaged with means on said aircraft and constrained in tow behind said aircraft, means on said aircraft for bringing said in tow cargo into juxtaposition with said aircraft and absorbing the energy of inertia of said cargo comprising a pick-up loop interconnected with said pick-up line, capstan means, drag means adapted to trail behind said aircraft, a tow line on said drag means reeved on said capstan means, integral first retaining means on said aircraft and second retaining means on said tow line releasably engaged with said first retaining means and adapted to be disengaged therefrom by the inertia of said cargo, said loop being interconnected with said second retaining means.

27. The invention defined in claim 26, wherein said capstan means further includes drag control means for selectively regulating the drag of said drag means.

28. The. invention defined in claim 26, wherein said first drag means comprises a parachute having a canopy and shroud lines, said shroud lines being connected with said extension of said pick-up loop, and wherein said capstan means further includes selective drag control ii i means for said first drag means comprising a control line connected at one end with the apex of said canopy and differential pay-out means on said capstan means, said control line being wound thereon at the other end thereof,

whereby said canopy can be selectively spilled to vary the drag exerted by said first drag means.

29. An-aerialpick-up system comprising an aircraft, a surface station, a cargo at said surface station to be line and'saidpick-up line adapted to interlock with said one-way engaging means.

37. 'In an aerial pick-up system including an aircraft, 'pick-up means'on said aircraft including energy absorbing .means, a surface station, an airborne target means tethered to said surface station, a cargo at said surface station to be' picked up by said aircraft, a pick up,lineconnectedto said cargo, a pilot line connected with said pick-up'line,

picked up and delivered to said aircraft while said aircraft is maintaining normal altitude and airspeed; first pick-up means on said aircraft including a dependent pickup loop, capstan means, first drag means adaptedto trail behind saidtaircraft, a tow line on said drag means reeved on said capstan'means, integral first'retaining means on releasably engaged with said first retaining means and adapted to be disengaged therefrom by the inertia ofsaid cargo, said loop being interconnected with said second retaining meansyand second pick-up means at said'su'rface station comprising anairborne target means tethered to said surface station, a pick-up line-connected with said said aircraft and second retaining mea'ns on said tow line E15 anda drag means interconnecting said pilot line and said airborne target means, said pilot line being tethered to said surface station to constrain said target means and said-drag means'thereabovq the method ofcpicking up 'said cargo with said aircraft-'comprisingthe steps of flying said aircraft directly into said target means and rupturing-said target means, engaging said pilot line with said pick-up-ine'ans at a point below'said drag means to I thereby reeve said pilot line around said pick-up means,

cargo, a pilot line connected with said pick-up line and second drag means interconnecting said pilot line and said target rneans, said pilot 'lineeb eing tethered to said 1 f: surface stationto constrain said target means and said drag means thereabove and b'ein gadapted to be engaged by said pick-up loop adjacent said second drag means.

30. The-invention'defined in claim 29, Whereinjsaid first andseconddrag means comprise firstand second.

parachute means, respectively, said first drag means being of sutficient size to accelerate said'pick-up linefand' accelerating said pick-up line toward said aircraft with said pilot line by the kinetic energy derived from said aircraft by said drag means, securing said pick-up line to said pick-up meansQrupturingsaid pilot: line to thereby release said-drag'meansp'absorbing the energy of inertia of said cargo with said energyabsorbing. means and subsequentlyaccelerating'said cargo toward' said aircraft by ,saidpick-up-line'. t 138.1 In an aerial pick-up 'sys'tem:including' anjaircraft,

' t 'pi'ck-upmeans on said 'aircraft including a pick-up loop,

said cargo toward said aircraft and said" second dragl means being of sutiicient size to accelerate saidfpick-up line and said pilot line towardfsaid' aircraft 31. The, invention" defined inclaim 29," whereinfsaid pilot line is' of substantially le'ssergstrengthtand weiglit than saidpick-up line and wherein {both saidxpilot lin'e 2f capstan means and first ,dr'ag means, said loop including an integralex'tension reeved on" said capstan means and connected with said firstdrag 1n'eans,,a surface "station, an

-.airborne.ttarget means tethered to said surface'station, a

cargo at said-surface station to be picked upand delivered :t'o'said aircraft, a pick-up line connectedfto said cargo, a

" pilot line connected with. said pick-up line, and a second and said tpicklp linerare composed of resilient synthetic fibers.- p V p v V 32. The invention define d in clai'mg2 9, wherein saidcapstan means furtherincludes selective Idrag control means for said; first .dr ag meanspf g p v t v 33. The invention defined 'i' claim l29, wherein'said V first drag'means comprises a parachute having a canopy and shroud lines, said'shroud lines being connected with v said"extension of said] pick-up loop, andwherein said} 1 capstan means further includes s'elctivej drag control,

means forssaid first drag rneanscomprising .ajcontrolline fconnected at one end with the apex' of'; said canopyand differential spay-out means on said capstan .rneans, 1 said i control line being wound thereon atthe other end thereof, whereby said canopy can be selectively spilled to vary the drag exerted bysaid first dragmeans; v x

34. The invention defined in claim .29, wherein said first pick-up means .further includes a one-Way brake means intermediate said pick-up loop and said capstan:

means. 7 I p i 35. The invention defi ned -in claim 29, wherein' said pick-up loop further i'nclu'des line guide means for-said pilot line and a first coupling means on said line, guide means, and wherein said second pick-up means: further 1 includes a second coupling means interconnecting ,said

pilot line and said pick-upline adapted to interconnect with said first coupling means' wh'en said pickaup line has been accelerated into juxtaposition with saidilineguide' means by said pilot line. t

36; The inventiondefined m 'claim 35, wherein said line guide means comprises a V-shaped tubularmember' integral with saidpick-up loopand adapted to receive said pilot line withinthe ape'xthcreof; wherein s'aidfir'sti "coupling means comprises an integral extension of the apexf of said \/-shaped member having one-way engaging-means thereon; and wherein-said second coupling meansincludes coupling lsmentlat; the juncture of saidgpilot .drag means interconnecting said pilot line and said air iborn'target means, saidtpilot'lineibeing tetheredto said surface station to constrain said target means andsaid I drag .meansthereabove,- the' method of picking up and "deliveringsaidrcargo to said aircraftrcomprising the steps 'offitrailing saidfir 'st'drag means behindsaid aircraft, flyfing said aircraft'directly'into: said target means and ra turing-said target means, engaging saidjpilotiline with said pick-up means at a point-belowsaid'second drag meansto thereby reeve-.said'pilot line around said pick-up means, accelerating said'pick-up line toward said aircraft with saidpilot'line?by the kinetic energy derived from said *aircraftbysaid seconddr ag' means, securing'said pick-up linelto said Ipick-upnneans; rupturing said fpilot line 'to thereby release'fsaid second {drag -means, absorbing the energy of inertia'of'said cargo with said first drag means and-subsequently paying out said first drag'means to cause saidpick-up loop to reeve around said capstanmeans and iaccelerate said cargo; into juxtaposition with'said aircraft.

39. In'a drag parachute system includinga capstan, a

Ydrag line reeved on said capstan-, and a parachute having a c'anopyrand shroud lines connected with-said drag line by said'shroud lines, drag control means? for said para- J chute comprising a control'line connected at one end'with I -t-heapex or said'c'an'op'yand differential pay-out means on said 'capstan means,saidcontrol line being wound onsaid differential payout means atthepther end thereof,- whereby; saidcanopy can beselectively spilled to vary I the v V I 7/31 L 2,334,979 11/43" 2,410,451 11/46 2,467,112; 4/49 '7 routs amass, was nram aar, 

1. AN AERIAL PICK-UP SYSTEM COMPRISING AN AIRCRAFT, A SURFACE STATION, FIRST PICK-UP MEANS ON SAID AIRCRAFT, A CARGO AT SAID SURFACE STATION TO BE DELIVERED ON SAID AIRCRAFT VIA SAID FIRST PICK-UP MEANS WHILE SAID CRAFT IS MAINTAINING NORMAL ALTITUDE AND AIRSPEED AND SECOND PICK-UP MEANS AT SAID SURFACE STATION ENGAGEABLE BY SAID FIRST PICK-UP MEANS, INCLUDING A PICK-UP LINE CONNECTED AT ONE END TO SAID CARGO, 